Automated tuning of gas turbine combustion systems

ABSTRACT

A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter.

CROSS-REFERENCE TO RELATED APPLICATION

The present application is a continuation of pending U.S. applicationSer. No. 13/855,220 which is a continuation of U.S. application Ser. No.12/463,060. The contents of U.S. application Ser. No. 13/855,220 filedon Apr. 2, 2013 and U.S. application Ser. No. 12/463,060 filed on May 8,2009 and issued on May 7, 2013 as U.S. Pat. No. 8,437,941 are herebyincorporated by reference in their entirety.

TECHNICAL FIELD

The present invention relates to an automated system to sense theoperating condition of a combustion system and to make presetadjustments to achieve desired operation of the turbine.

BACKGROUND

Lean premixed combustion systems have been deployed on land based gasturbine engines to reduce emissions, such as NOx and CO. These systemshave been successful and, in some cases, produce emission levels thatare at the lower limits of measurement capabilities, approximately 1 to3 parts per million (ppm) of NOx and CO. Although these systems are agreat benefit from a standpoint of emission production, the operationalenvelope of the systems is substantially reduced when compared to moreconventional combustion systems. As a consequence, the control of fuelconditions, distribution and injection into the combustion zones hasbecome a critical operating parameter and requires frequent adjustment,when ambient atmospheric conditions, such as temperature, humidity andpressure, change. The re-adjustment of the combustion fuel conditions,distribution and injection is termed tuning.

Controlled operation of a combustion system generally employs a manualsetting of the operational parameters of a combustor at an averageoperational condition. These settings are satisfactory at the time ofthe setup, but conditions may change and cause an unacceptable operationin a matter of hours or days. Other approaches use a formula to predictemissions based on gas turbine operating parameters and select a setpoint for fuel distribution and/or overall machine fuel/air ratio,without modifying other parameters, such as fuel gas temperature. Theseapproaches do not allow for timely variation, do not take advantage ofactual dynamics and emission data or do not modify fuel distribution,fuel temperature and/or other turbine operating parameters.

Another variable that impacts the lean premixed combustion system isfuel composition. Sufficient variation in fuel composition will cause achange in the heat release of the lean premixed combustion system. Suchchange may lead to emissions excursions, unstable combustion processes,or even blow out of the combustion system.

Mis-operation of the combustion system manifests itself in augmentedpressure pulsations or an increase in combustion dynamics. Pulsationscan have sufficient force to destroy the combustion system anddramatically reduce the life of combustion hardware. Additionally,improper tuning of the combustion system can lead to emission excursionsand violate emission permits. Therefore, a means to maintain thestability of the lean premixed combustion systems, on a regular orperiodic basis, within the proper operating envelope, is of great valueand interest to the industry. Additionally, a system that operates byutilizing near real-time data, taken from the turbine sensors, wouldhave significant value to coordinate modulation of fuel distribution,fuel gas inlet temperature and/or overall machine fuel/air ratio.

SUMMARY OF THE INVENTION

The present invention is a controller and method for tuning theoperation of a gas turbine of the type having sensors for measuringoperational parameters of the turbine and controls for controllingvarious operational elements of the turbine. The operational parametersof the turbine which are received by the controller may include one ormore of the following: combustor dynamics, turbine exhaust temperature(overall fuel/air ratio) and turbine exhaust emissions. The operationalcontrol elements may include one of more of the following: fueldistribution, fuel temperature and turbine exhaust temperature. Theturbine/power plant system also includes a communication link, such as adistributed control system (DCS). The link permitting communication withthe sensors and the operational controls. The tuning controller is alsoconnected to the turbine system through the communication link.

The controller operates by receiving data from the sensors. Operationalpriorities for the turbine may be set within the controller and aretypically selected from optimum NOx emissions, optimum power outputand/or optimum combustor dynamics. The data received from the turbinesensors is compared to stored operational standards within thecontroller. The selected operational standards are preferably based onthe set operational priorities. A determination is made as to whetherthe turbine operation conforms to the operational standards. Inaddition, upon the data being determined to be out of conformance, afurther determination is made of the dominant tuning criteria again.This further determination is preferably based on the preset operationalpriorities. Once the logical determinations are made, the tuningcontroller communicates with the operational control means through thecommunication link to perform a selected adjustment in an operationalparameter of the turbine. The selected operational adjustment ispreferably based on the dominant tuning criteria and has a preset fixedincremental value and defined value range. Each incremental change ispreferably input over a set period of time, which is sufficient for theturbine to gain operational stability. Once the time period passes,operational data is again received from the turbine sensor means todetermine if an additional incremental change is desired. Uponcompleting the adjustments within a defined range, a further operationalparameter adjustment is selected, again preferably based on the dominanttuning criteria, and a further fixed incremental adjustment is made. Thetuning process continues by the controller receiving operational data todetermine if the operation is conforming to the operational standards orwhether an additional adjustment is required. The operational parametersbeing adjusted by the tuning controller may include one or more of thefollowing: the combustor fuel distribution split within the nozzles ofthe combustor, the fuel gas inlet temperature, and/or the fuel/air ratiowithin the turbine.

In a further aspect of the invention, the system performs a method fordetermination of the dominant gas turbine combustion system tuningscenario through the use of Boolean hierarchical logic and multiplelevels of control settings.

In another aspect of the invention, the method performed relates to andautomated control of the gas turbine inlet fuel temperature throughautomated modification of the fuel gas temperature control set pointwithin a Distributed Control System (DCS).

In a still further aspect of the invention, a method for automatedcontrol of a gas turbine inlet fuel temperature is defined by automatedmodification of the fuel gas temperature control set point within thefuel gas temperature controller.

In another aspect of the invention a method for communicating turbinecontrol signals to a gas turbine controller is accomplished through theuse of an existing gas turbine communication link with an externalcontrol device, such as, for example a MODBUS Serial or Ethernetcommunication protocol port existing on the turbine controller forcommunication with the a Distributed Control System (DCS).

In a still further aspect of the invention a method for modification ofa gas turbine combustion system is defined by a series of auto tuningsettings via a user interface display, which utilizes Boolean-logictoggle switches to select user-desired optimization criteria. The methodis preferably defined by optimization criteria based on OptimumCombustion Dynamics, whereby toggling of this switch changes themagnitude of the combustor dynamics control setting(s).

BRIEF DESCRIPTION OF DRAWINGS

For the purpose of illustrating the invention, the drawings show formsthat are presently preferred. It should be understood that the inventionis not limited to the precise arrangements and instrumentalities shownin the drawings of the present invention.

FIG. 1 shows a schematic representation of an operational plantcommunication system encompassing the gas turbine engine system,incorporating a gas turbine tuning controller.

FIG. 2 shows a functional flow chart for a tuning controller of thepresent invention.

FIG. 3 shows a user interface display for selecting the optimizationmode within the present invention.

FIG. 4 shows a schematic of the inter-relationship of variousoptimization mode settings.

FIGS. 5-8 show operational examples of operational tuning of a gasturbine engine system as contemplated by the present invention.

FIGS. 9A and 9B are schematic representations of the function of thetuning controller of the present invention in maintaining the tuning ofthe turbine system.

DETAILED DESCRIPTION

FIG. 1 is a communication diagram for a gas turbine engine (not shown),within which a tuning controller 10 of the present invention operates. Acommunication link or hub is provided to direct communication betweenvarious elements of the turbine system. As shown, the communication linkis a Distributed Control System (DCS) identified by the numeral 20. Mostof the turbine control is performed through the DCS 20. A turbinecontroller 30 communicates directly with the gas turbine and with theDCS 20. In the present invention, information relevant to turbineoperation, e.g., turbine dynamics, turbine exhaust emissions, etc. aredirected through the DCS 20 to the tuning controller 10. The tuningcontroller 10 is contemplated to be a stand-alone PC used to run as aprogrammable logical controller (PLC). The tuning controller 10 ispreferably a separate computer from the turbine controller 30 and doesnot communicate directly with the turbine controller 30, except throughthe DCS 20. The signals from the tuning controller 10 may be transferredto the turbine controller 30 or other controls within the system by theuse of an external control device, such as a MODBUS Serial or Ethernetcommunication protocol port existing on or added to the system.

The relevant operational data is received from sensor means associatedwith the turbine. For example, the turbine exhaust emission reading istaken from stack emissions by a continuous emissions monitoring system(CEMS) 40, which is connected to the DCS. Combustion dynamics is sensedusing a dynamic pressure sensing probe located within the combustionregion of the turbine combustor. As shown, a continuous dynamicsmonitoring system (CDMS) 50 is provided and communicates with the DCS.The CDMS 50 preferably uses either direct mounted or wave guideconnected pressure or light sensing probes to measure the combustiondynamics. Another relevant operational parameter is the fuel gastemperature. Again, this temperature information is directed to thetuning controller 10 through the DCS 20 from the fuel heating unit 60.Since part of the tuning operation may include adjustment of the fueltemperature, there may be a two-way communication between the tuningcontroller 10 and the fuel heating unit 60.

Relevant operational data from the turbine is collected several timesper minute. This data collection allows for near real-time systemtuning. Most relevant turbine operational data is collected by thetuning controller in near real-time. However, the turbine exhaustemissions is typically received from the sensor by the tuning controller10 with a 2 to 8 minute time lag from current operating conditions. Thistime lag necessitates the need for the tuning controller 10 to receiveand buffer relevant information, for a similar time lag, before makingoperational tuning adjustments. The tuning controller 10 tuningadjustment time lag assures that all of the operational (includingexhaust emissions) data is representative of a stable turbine operationbefore and after any adjustments have been made. Once the data is deemedstable, the tuning controller 10 determines whether there is a need foradjustment of tuning parameters. If no adjustment is necessary, thetuning controller 10 maintains the current tuning and waits to receivethe next data set. If changes are desired, tuning commences.

All determinations of the need for turbine tuning are performed withinthe tuning controller 10. The tuning operation is started based on an“alarm” created by receipt of operational data outside of presetoperational criteria. In order for the tuning operation to be initiated,the alarm—and thus the data anomaly—must continue for a predeterminedperiod of time.

One example of a tuning adjustment is the variation of the fuel nozzlepressure ratio to adjust combustion dynamics. With the requirement ofhigher firing temperatures to achieve greater flame temperatures andefficiency, turbine combustors must release more energy in a givencombustor volume. Better exhaust emissions are often achieved byincreasing the mixing rate of fuel and air upstream of the combustionreaction zone. The increased mixing rate is often achieved by increasingthe pressure drop at the fuel nozzle discharge. As the mixing rateincreases in combustors, the turbulence generated by combustion oftenleads to noise within the combustor and may lead to the generation ofacoustic waves. Typically, acoustic waves are caused when the soundwaves of the combustion flames are coupled with the acousticcharacteristics of the combustor volume or the fuel system itself.

Acoustic waves may affect the internal pressure in the chamber. Wherepressure near a fuel nozzle rises, the rate of fuel flowing through thenozzle and the accompanying pressure drop decreases. Alternatively, adecrease in pressure near the nozzle will cause an increase in fuelflow. In cases where a low fuel nozzle pressure drop allows fuel flowoscillation, a combustor may experience amplified pressure oscillations.To combat the pressure oscillations within the combustor, combustiondynamics are monitored and the fuel air ratio and fuel nozzle pressureratio may be modified to reduce or eliminate unwanted variations incombustor pressure, thereby curing an alarm situation or bringing thecombustion system back to an acceptable level of combustion dynamics.

As shown in FIG. 2, the data received from the sensing means for thecombustor dynamics (50), turbine exhaust emissions (40), and otherrelevant turbine operating parameters (30) are directed through the DCS20 to the tuning controller 10. These input values are then compared tostandard or target operational data for the turbine. The storedoperational standards are based, at least in part, on the operationalpriority settings for the turbine. These priority settings are definedon the main user interface 12 of the tuning controller 10 and are showngraphically in FIG. 3. Based on the priority settings, a series ofadjustments are made to the operation of the turbine by the turbinecontroller 10 connected through the DCS 20. The adjustments are directedto the control means, including the fuel heating unit 60 (FIG. 1) andvarious other operational elements 80 of the turbine (FIG. 2).

The interface display 12 shown in FIG. 3 is comprised of switches (eachhaving an On/Off indication). These switches allow the user to specifythe desired tuning priorities for the operation of the turbine. Theswitched operational priorities include optimum NOx emissions 14,optimum power 16 and optimum combustor dynamics 18. Each of theseswitches is set by the user to adjust the preferred operation of theturbine. Within the tuning controller are functions that operate withinthe priorities set by the switches. Preferably, if both the optimum NOxemissions switch 12 and the optimum power switch 14 are set to “On”, thecontroller 10 will run in the optimum NOx mode, not optimum power. Thus,to run in optimum power mode, the optimum NOx emissions switch 12 mustbe “Off”. FIG. 4 shows a graphical representation of theinterrelationship of the interface display switches.

Returning to FIG. 2, there is shown a representation of the logical flowof the determinations and calculations made within the tuning controller10. The tuning controller 10 receives the actual operating parameters ofthe turbine through the turbine controller 30, combustor dynamicsthrough the CDMS 50, and the turbine exhaust emissions through the CEMS40. This sensor data is directed to the tuning controller 10 through theDCS 20. The received sensor data is compared to stored operationalstandards to determine if the turbine operation is conforming to thedesired settings. The operational standards are based on the presetoperational priorities of the turbine, defined by the switches 14, 16,18 on the main user interface display 12 of the tuning controller 10(FIG. 3).

Based on the preset operational priorities, a hard-coded hierarchicalBoolean-logic approach determines the dominant tuning criteria based onoperational priorities. From this logical selection, the tuningcontroller 10 implements a fixed incremental adjustment value forchanging an operational parameter of the turbine within a maximum rangeof adjustment (e.g., high and low values). The tuning changes are madein a consistent, pre-determined direction over a pre-determinedincrement of time and are dependant on the dominant tuning criteria atpresent. It is contemplated that no formulaic or functional calculationsare made to determine tuning adjustments; rather, the incrementaladjustments, the direction of the adjustments, the time span betweenadjustments, and the maximum range for the adjustments for eachparameter and for each tuning criteria are stored in the tuningcontroller 10.

As shown in FIG. 2, the tuning controller 10 determines whether theemissions are in compliance 100 and whether the combustor dynamics areat acceptable levels 102. If both are in compliance with the setoperational standards, the tuning controller 10 waits for the next dataset from the CEMS 40 or the CDMS 50, or for other operational data 80.If the received data is non- conforming with the operational standards104, the tuning operation moves to the next tuning step. The logicaladjustment of turbine operation is defined by the dominant tuningcriteria 106, which is based at least in part on the preset operationalpriorities set within the user interface 12.

In a preferred operation, the tuning controller 10 will first attempt tochange the turbine combustor fuel splits 108. The fuel split determinesthe distribution of the fuel flow to the fuel nozzles in each combustor.If these adjustments do not resolve the tuning issue and do not placethe operational data back into conformance with the operationalstandards, a further adjustment is performed. In certain situations, thenext incremental adjustment may be a change of the fuel gas temperatureset point. In this adjustment step, the tuning controller 10 sends amodified fuel gas inlet temperature signal to the DCS 20, which isdirected to the fuel heating unit 60.

If modification of the combustor fuel splits and/or fuel gas inlettemperature does not resolve the tuning issue 110, the tuning controller10 will then alter the overall fuel/air ratio 112. This approach makeschanges to the turbine thermal cycle utilizing fixed incremental changesover pre-determined amounts of time. This step is intended to adjust theexhaust temperature (up or down) by adjusting the air to fuel ratio inaccordance with predetermined, standard control curves for the turbineoperation, which are maintained within the memory of the tuningcontroller 10.

In the present invention, it is contemplated that all control changesdirected by the tuning controller are fed back to the turbine systemthrough the DCS. These changes are implemented directly within thevarious controller means within the system or through the turbinecontroller. When the operational data is returned to the desiredoperational standards, the tuning settings are held in place by thetuning controller pending an alarm resulting from non- conforming datareceived from the sensor means through the DCS.

The adjustments sent from the tuning controller to the turbinecontroller or the associated controller means are preferably fixed inmagnitude. Thus, the adjustments are not recalculated with new data oroptimized to a target. The adjustments are part of an “open loop”. Oncestarted, the adjustments move incrementally to the preset maximum ormaximum within a specified range, unless an interim adjustment placesthe operation data into conformance with the operational standards.Under most circumstances, when the full incremental range for oneoperational parameter is completed, the tuning controller moves on tothe next operational parameter, which is defined by the presetoperational priorities. The logic of the tuning controller drives theoperational parameter adjustment based on a “look-up” table storedwithin the memory of the tuning controller and preset operationalpriorities.

The tuning controller preferably addresses one operational parameter ata time. For example, the dominant tuning criteria dictates the firstadjustment to be made. In the preferred example discussed above, thefuel distribution/split parameter is first adjusted. As indicated inFIG. 2, the fuel split of fuel circuit 1—the center nozzle in thecombustor—is first addressed, followed by the split for fuel circuit2—the outer nozzles in the combustor. The fuel gas inlet temperatureadjustment generally follows the fuel split adjustments when needed.Within each step, there is an incremental adjustment, followed by a timelag to permit the adjusted turbine operation to stabilize. After thetime lag, if the current operational data analyzed by the tuningcontroller indicates that turbine operation still remains outside of theoperational standards, the next incremental adjustment is made. Thispattern repeats for each step. Under most circumstances, only when oneadjustment step is completed does the tuning controller move onto thenext operational parameter.

The tuning controller preferably controls combustion operation tomaintain proper tuning in variable conditions of ambient temperature,humidity and pressure, all of which vary over time and have asignificant effect on turbine operation. The tuning controller may alsomaintain the tuning of the turbine during variation in fuel composition.Variation in fuel composition may cause a change in the heat release,which can lead to unacceptable emissions, unstable combustion, or evenblow out. The tuning controller preferably does not serve to adjust fuelcomposition to compensate; rather, it tunes the operational parameters(fuel gas distribution, fuel gas inlet temperature, and/or turbinefuel/air ratio) to address the effects on combustion output anddischarge.

In other tuning dynamics, an alternate order for the adjustments iscontemplated. For example, if the dominant operational priority isoptimum NOx emissions, the fuel temperature adjustment may be skipped,going directly to the operational control curves. If, however, dynamicsis the operational priority (and the optimum NOx emission switch 14 isOff), the incremental fuel temperature adjustment may be performedbefore going to the operational control curves. Alternatively, the stepof making adjustments in accordance with the operational control curvesmay be turned off completely.

In FIGS. 5-8, there is shown various operational examples of the tuningoperation of a tuning controller of the present invention based onoperational data from a running turbine system. In FIG. 5, a change inthe combustor fuel split is accomplished in reaction to a dynamics alarmis generated when the combustor dynamics moves outside of the setoperational priorities for optimum dynamics. The actual combustordynamics data received from, for example, the CDMS 50 is designated asCD in the graph. The moving average for the combustor dynamics isidentified in the graph as ACD. When the combustor dynamics exceeds thedynamics limit value DL for a set period of time TA an alarm goes offwithin the tuning controller. This alarm causes the first event E1 and aresulting incremental adjustment in the combustor fuel split tuningparameter. As illustrated, the incremental increase in the fuel splitcauses a corresponding drop in the combustor dynamics CD, with theaverage combustor dynamics ACD dropping below the dynamics alarm limitDL. As time continues, the tuning is held by the tuning controller andthe average combustor dynamics ACD maintains its operational positionbelow the dynamics limit DL. Thus, no further adjustments necessary oralarms issued.

In FIG. 6, the tuning criteria is NOx emissions. As NOx emissions dataNE is received from the tuning controller, an alarm is generated afterthe passage of time TA. The alarm is caused by the NOx emissions NEexceeding the operational standard or tuning limit EL. The alarmactivates a first event E1 resulting in an incremental increase in thefuel split FS. After a period of time T2 from the first event E1, theNOx alarm is still activated due to the NOx emissions NE exceeding thepreset tuning limit EL. This continued alarm after time T2 causes asecond event E2 and a second incremental increase in the fuel splitvalue FS. This second increase is equal to the first incrementalincrease. The second event E2 causes the NOx emissions NE to drop belowthe preset limit EL within the review time period and halts the alarm.As the NOx emissions NE remains below the limit EL, the fuel split FStuning is held and the operation of the turbine continues with thedefined operational parameters.

In FIG. 7, the tuning criteria is again NOx emissions, with the alarmcreated by a low reading received by tuning controller. As shown, theNOx tuning limit NL is defined. Upon passage of the set time period fromreceiving data, the alarm is generated and a first event E1 occurs. Atthe first event E1, the fuel split is incremental adjust downward. Aftera set passage of time from event E1 additional emissions data NE isreceived and compared to the preset limit EL. Because the NOx is stillbelow the alarm level EL, a second event E2 occurs resulting in afurther reduction in the fuel split value FS. A further passage of timefrom event E2 occurs and additional data is received. Again, the NOxdata is low, maintaining the alarm and resulting in a further event E3.At event E3, the fuel split value FS is again reduced by the sameincremental amount. This third incremental adjustment results in the NOxemissions NE rising above the preset limit EL and results in removal ofthe alarm. The fuel split FS tuning value set after event E3 is held inplace by the tuning controller.

In FIG. 8, the NOx emissions data NE received by the tuning controlleris again tracking along the lower emissions limit EL. At the firsttuning event E1, the fuel split value FS is incrementally dropped toresult in a corresponding increase in the NOx emissions NE over thelower limit EL. After this first incremental adjustment, the NOxemissions for a period of time holds above the limit EL and then beginsto again fall. At the second tuning event E2, the fuel split value FS isagain adjusted by the designated fixed incremental value. This secondadjustment then places the fuel split value FS at its defined minimumwithin the preset range of values. This value limit moves the tuningoperation to the next operational parameter, which is normally thesecond fuel circuit adjustment. In the example provided, this secondcircuit value (not shown) is already at its set maximum/minimum. Thus,the tuning operation moves on to the next operational parameter. Thetuning operation moves to the load control curves. As shown, at event E2an incremental adjustment is made in the load control curve value LC.The increase in the LC value results in a corresponding increase in theNOx emission to a value above the minimum EL and removes the alarm. Uponremoval of the alarm, the tuning settings are held and no furtheradjustments are made. The tuning controller then proceeds to receivedata from the sensor means, through the DCS, and continues to makecomparisons with the set operational standards (including the minimumNOx emissions limit EL).

FIGS. 9A and 9B are schematic representations of the operation of thetuning controller within contemplated invention. The operation of theturbine is defined by the emission output of the turbine, both NOx andCO, turbine dynamics and flame stability. In FIG. 9A, a tuned system isdefined by a preferred operating envelope in the center of theoperational diamond. This preferred operational envelope is typicallymanually set based on a prior start-up or operation of the turbinesystem. However, weather changes, both hot and cold, and mechanicalchanges within the turbine system cause a drift within the operationaldiamond. Hence a tuning is desired so as to maintain the turbineoperation within the preferred range. In FIG. 9B, a defined buffer ormargin is set within the operational diamond to serve as a warning for adrift of the turbine operation outside of the preferred operationalenvelope. Once one of the sensed operational values reaches the definedbuffer line or limit, an alarm is generated, causing a tuning event.Based on the direction of the drift, the tuning controller creates apreset reaction to meet the specifics of the tuning need. This presetreaction is a defined incremental shift in an operational parameter ofthe turbine as a means for moving the turbine operational envelope backinto the desired range, and away from the buffer limit.

The present invention has been described and illustrated with respect toa number of exemplary embodiments thereof. It should understood by thoseskilled in the art from the foregoing that various other changes,omissions and additions may be made therein, without departing from thespirit and scope of the present invention, with the scope of the presentinvention being described by the foregoing claims.

1. A system for tuning the operation of a gas turbine, the turbinehaving sensors for measuring operational parameters of the turbine, theoperational parameters including combustor dynamics, and turbine exhaustemissions, the turbine also having operational controls for adjustingvarious operational control elements of the turbine, the operationalcontrol elements comprising one or more of turbine fuel distributionsplits, inlet fuel temperature, and fuel-air ratio, and a communicationlink for the sensors and controls, the system comprising: a controllercommunicating with the sensors and the controls, the controller tuningthe operation of the turbine in accordance with the following: receivingreal-time or near real-time operational data regarding the operationalparameters including combustor dynamics and turbine exhaust emissionsfrom the sensors, comparing the operational data to stored operationalstandards and determining if turbine operation conforms to theoperational standards, the operational standards based on one or moretuning priorities, communicating with the operational controls toperform a selected adjustment in an operational control element of theturbine, receiving operational data from the sensors upon communicatingthe selected adjustment to determine if an additional incrementaladjustment is desired, and upon completing a series of incrementaladjustments, selecting a further operational parameter adjustment, andreceiving operational data from the sensors upon further operationaladjustment to determine if still further adjustment is desired.
 2. Thesystem of claim 1, wherein the adjustments in the operational controlelements of the turbine are selected from the group comprising combustorfuel distribution split within the nozzles of the combustor, fuel gasinlet temperature, and fuel-air ratio within the turbine.
 3. The systemof claim 1, wherein the tuning by the controller further comprisessetting the one or more tuning priorities for turbine operation, the oneor more tuning priorities comprising one or more of optimum NOxemissions, optimum power output and optimum combustor dynamics.
 4. Thesystem of claim 3, wherein the tuning by the controller furthercomprises selecting the stored operational standards for the turbineoperation based on the set tuning priorities.
 5. The system of claim 3,wherein the tuning by the controller further comprises determining thedominant tuning criteria for non-conforming operation of the turbine,the dominant tuning criteria based on the set tuning priorities.
 6. Thesystem of claim 1, wherein the controller communicates with the turbinesensors and controls through a distribution control system (DCS).
 7. Thesystem of claim 1, wherein the controller selects an operational controlelement adjustment having a fixed incremental value.
 8. The system ofclaim 7, wherein the incremental control element adjustments selected bythe controller occur within a defined range.
 9. The system of claim 7,wherein each incremental adjustment is input over a defined period oftime sufficient for the turbine to gain operational stability.
 10. Thesystem of claim 9, wherein the defined period of time is fixed.
 11. Thesystem of claim 7, wherein the tuning by the controller furthercomprises determining the dominant tuning criteria for non-conformingoperation of the turbine, the dominant tuning criteria based on the settuning priorities for the turbine.
 12. The system of claim 11, whereinthe selected incremental adjustment of an operational control elementvalue is based on the dominant tuning criteria.
 13. The system of claim1, wherein the further selected adjustment includes a fixed incrementalvalue occurring within a defined range, with each further incrementaladjustment made over a set period of time sufficient for the turbine togain operational stability.
 14. The system of claim 1, wherein thefurther operational parameter is selected based on a dominant tuningcriteria as determined by the controller.
 15. The system of claim 3,wherein the tuning by the controller further comprises specifying theoptimum power output, wherein the specifying comprises selecting orde-selecting the optimum power output and wherein the specifyingoperates to change the stored operational standards.
 16. A controllersystem for tuning the operation of a gas turbine, the turbine havingsensor means for measuring operational parameters of the turbine, theoperational parameters including stack emissions and combustion dynamicsfrom the turbine, control means for controlling various operationalcontrol elements of the turbine, the operational control elementscomprising one or more of fuel distribution splits, fuel-air ratio andinlet fuel temperature, and a communication link for the sensor meansand the operational element control means, the controller systemcomprising: means for setting tuning priorities of the turbine forturbine operation, the one or more tuning priorities comprising one ormore of the group comprising optimum NOx emissions, optimum power outputand optimum combustor dynamics, receiving means for communicating withthe sensor means to receive turbine operational data in real-time ornear real-time, means for comparing the received data to a set ofpredetermined allowable values based on the set tuning priorities andfor determining whether tuning adjustment is required, directing meansfor communicating with the control means to perform a definedincremental adjustment in a selected operational control elementcontrolled by the control means, and means for determining if theincremental adjustment conforms the turbine operation to the set valuesor if performing further adjustment is required.
 17. A system for tuningthe operation of a gas turbine, the turbine having sensor means formeasuring operational parameters of the turbine, the operationalparameters including stack emissions, and combustion dynamics controlmeans for controlling various operational control elements of theturbine, the operational control elements comprising one or more of fueldistribution splits, inlet fuel temperature and fuel-air ratio, and acommunication link between the sensor means and the operational elementcontrol means, the system comprising: a computer controllercommunicating through the communication link to the sensor means and thecontrol means, the computer controller tuning the operation of theturbine in accordance with the following receiving operational data fromthe turbine sensor means in real-time or near real-time, comparing theoperational data to stored operational standards and determining ifadjustment of the operational control means is necessary, upondetermination of a required adjustment, communicating with theoperational control means through the communication link to perform adefined incremental adjustment in an operational parameter of theturbine, and receiving operational data from the turbine sensor meansregarding the adjusted operation of the turbine and comparing theoperational data to the stored operational standards to determine if afurther incremental adjustment in an operational parameter is necessary.18. A method of tuning the operation of a gas turbine, the turbinehaving sensors for measuring operational parameters of the turbine, theoperational parameters including stack emissions and combustiondynamics, controls for controlling various operational control elementsof the turbine, the operational control elements comprising one or moreof fuel distribution splits, inlet fuel temperature and fuel-air ratio,and a distributed control system (DCS) communicating with the sensormeans and the operational element control means, the method comprising:establishing a communication link with the DCS and receiving dataregarding the operational parameters from the sensors, comparing datareceived in real-time or near real-time to set standards to determine ifadjustment to an operational control element is desired, communicatingwith the DCS to perform a defined incremental adjustment in anoperational control element of the turbine that is controlled by thecontrols, and receiving additional data through the DCS regarding theoperational parameters of the turbine from the sensors and determiningif the adjustment conforms turbine operation to the set standards or ifa further incremental adjustment is desired.